CN216123410U - Novel aerospace control module identification piece case - Google Patents
Novel aerospace control module identification piece case Download PDFInfo
- Publication number
- CN216123410U CN216123410U CN202122744399.2U CN202122744399U CN216123410U CN 216123410 U CN216123410 U CN 216123410U CN 202122744399 U CN202122744399 U CN 202122744399U CN 216123410 U CN216123410 U CN 216123410U
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- Prior art keywords
- wall
- case
- threaded rod
- heat dissipation
- control module
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- 230000017525 heat dissipation Effects 0.000 claims abstract description 41
- 230000002457 bidirectional effect Effects 0.000 claims description 61
- 230000006978 adaptation Effects 0.000 claims description 7
- 239000000428 dust Substances 0.000 abstract description 7
- 238000010276 construction Methods 0.000 abstract description 2
- 238000007664 blowing Methods 0.000 abstract 1
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 9
- 238000001816 cooling Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model relates to the technical field of construction frames, in particular to a novel aerospace control module identification piece case, which comprises a case, wherein a U-shaped heat dissipation case is connected to the upper part of the case in a buckling manner, a heat dissipation fan is arranged in the U-shaped heat dissipation case, the novel aerospace control module identification piece case is convenient for timely dissipating heat of the interior of the case, firstly, when one side of a mounting plate is pushed to be clamped on the outer wall of the case, a filter screen covers heat dissipation holes to filter dust in the air, the problem that the heat dissipation holes are blocked by the dust to prevent the heat from being dissipated out is avoided, further, the heat dissipation efficiency is reduced, when the heat in the case is slowly increased, the work of a heat dissipation fan can be controlled, the air blown by the heat dissipation fan enters the interior of the case through an air inlet hole, and the heat in the interior of the case can be timely dissipated by continuously blowing cold air by the heat dissipation fan through the heat dissipation holes, the damage of the aerospace control module caused by high temperature is avoided.
Description
Technical Field
The utility model relates to the technical field of construction frames, in particular to a novel aerospace control module identification piece case.
Background
The aviation control module identification machine case is a special control module case applied to aviation and aerospace, is usually one of necessary assembly components of related aviation control module equipment, and is internally provided with a power supply control part, a structural part and the like, a control system element unit and the like.
When current quick-witted case is using, because the long-time operation of inside control module equipment, the entering can lead to quick-witted incasement portion's high temperature, and the heat dissipation of machine case usually only dispels the heat at the louvre that the machine case outer wall was seted up, and is not clear for a long time, and the louvre can be blockked up by the dust in the air, can lead to the heat of quick-witted incasement portion to in time dispel the heat, piles up in quick-witted incasement portion, leads to high temperature to cause the damage to control module equipment, influences its life.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a novel case for an aerospace control module identification part, and aims to solve the problems that when the existing case is used, the temperature inside the case is overhigh due to the fact that internal control module equipment runs for a long time, the internal temperature is overhigh, the heat dissipation of the case is generally performed only through heat dissipation holes formed in the outer wall of the case and cannot be cleaned for a long time, the heat dissipation holes are blocked by dust in the air, the heat inside the case cannot be dissipated in time, the heat is accumulated inside the case, the control module equipment is damaged by high temperature, and the service life of the control module equipment is influenced.
In order to achieve the purpose, the utility model provides the following technical scheme: a novel aerospace control module identification piece chassis comprises a chassis;
the top buckle of machine case is connected with U type heat dissipation case, U type heat dissipation incasement portion installs radiator fan, just machine case outer wall set up with the fresh air inlet of U type heat dissipation case looks adaptation, machine case outer wall buckle is connected with two sets of mounting panels, and is two sets of fixedly connected with filter screen between the mounting panel, just machine case outer wall set up with the louvre of filter screen looks adaptation.
Preferably, the inside of the case is fixedly connected with a first supporting plate, a first bidirectional threaded rod is rotatably connected above the first supporting plate, the outer wall of the first bidirectional threaded rod is sequentially in threaded connection with a group of first moving blocks, one side of each first moving block is fixedly connected with a first L-shaped connecting rod, and one end of each first L-shaped connecting rod is fixedly connected with a first clamping block.
Preferably, the outer wall of the first bidirectional threaded rod is fixedly connected with a driving wheel, the outer wall of the driving wheel is rotatably connected with a belt, the driving wheel is rotatably connected with a driven wheel through the belt, the inner wall of the driven wheel is fixedly connected with a second bidirectional threaded rod, the outer wall of the second bidirectional threaded rod is sequentially in threaded connection with a group of second moving blocks, one side of each second moving block is fixedly connected with a second L-shaped connecting rod, one end of each second L-shaped connecting rod is fixedly connected with a second clamping block, the tail end of the second bidirectional threaded rod is rotatably connected with a second supporting plate, and one side of the second supporting plate is fixedly connected with the inner wall of the case.
Preferably, first backup pad inner wall sliding connection has the slide bar, slide bar one end fixed connection has the gag lever post, just the gag lever post outer wall with first backup pad inner wall sliding connection, gag lever post one end with first bidirectional threaded rod outer wall buckle is connected.
Preferably, a first clamping groove matched with the U-shaped heat dissipation box is formed in the upper portion of the case, one end of the U-shaped heat dissipation box is inserted into the first clamping groove, a second clamping groove matched with the mounting plate is formed in the outer wall of the case, and the tail end of the mounting plate is inserted into the second clamping groove.
Preferably, the outer wall of the first bidirectional threaded rod is respectively provided with a first thread groove and a second thread groove, the first thread groove and the second thread groove are opposite threads, the outer wall of the first supporting plate is provided with a first rotating groove matched with the first bidirectional threaded rod, and the tail end of the first bidirectional threaded rod extends into the first rotating groove.
Preferably, the outer wall of the second bidirectional threaded rod is respectively provided with a third thread groove and a fourth thread groove, the third thread groove and the fourth thread groove are opposite threads, the outer wall of the second support plate is provided with a second rotating groove matched with the second bidirectional threaded rod, and the tail end of the second bidirectional threaded rod extends into the second rotating groove.
Preferably, the inner wall of the first supporting plate is provided with a sliding groove matched with the sliding rod, one end of the sliding rod extends into the sliding groove, the outer wall of the first bidirectional threaded rod is provided with a limiting groove matched with the limiting rod, and one end of the limiting rod is inserted into the limiting groove.
Compared with the prior art, the utility model has the beneficial effects that:
1. the heat dissipation efficiency is reduced by the fact that the heat dissipation holes are blocked by dust to prevent heat from being dissipated out, when the heat in the case rises slowly, the heat dissipation fan can be controlled to work, the cooling fan blows air to enter the case through the air inlet hole, and the heat in the case can be dissipated timely by the fact that the cooling fan blows out cool air continuously to discharge the heat in the case through the heat dissipation holes, and the aerospace control module is prevented from being damaged by high temperature;
2. the space flight control module clamping device is convenient to clamp and fix space flight control modules of different models through a first bidirectional threaded rod, a driving wheel, a belt, a driven wheel, a first moving block, a first clamping block, a second bidirectional threaded rod, a second moving block and a second clamping block, the first bidirectional threaded rod is rotated to drive the first moving block to move in the opposite direction, the first moving block is also driven to move while moving, the first clamping block is moved to clamp and fix one end of the space flight control module, the first bidirectional threaded rod is also driven to rotate while moving, the driving wheel drives the driven wheel to rotate through the belt, the driven wheel drives the second bidirectional threaded rod to rotate, the second bidirectional threaded rod drives the second moving block to move in the opposite direction, the second moving block drives the second clamping block to move, and the second clamping block is moved to clamp and fix the other end of the space flight control module, the problem that the space flight control model is damaged due to shaking caused by external pressure is avoided.
Drawings
FIG. 1 is a schematic structural view of the present invention;
fig. 2 is an internal view of the first support plate of the present invention.
In the figure: 1. a chassis; 2. a first bidirectional threaded rod; 3. a driving wheel; 4. a belt; 5. a driven wheel; 6. a first moving block; 7. a first L-shaped connecting rod; 8. a first clamping block; 9. a first support plate; 10. a chute; 11. a slide bar; 12. a restraining bar; 14. a second bidirectional threaded rod; 15. a second moving block; 16. a second L-shaped connecting rod; 17. a second clamp block; 18. a second support plate; 20. a U-shaped heat dissipation box; 21. a heat radiation fan; 22. an air inlet hole; 23. heat dissipation holes; 24. mounting a plate; 25. and (4) a filter screen.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Examples
Referring to fig. 1-2, there are shown: the embodiment is a preferred implementation manner in the technical scheme, and a novel aerospace control module identification piece case comprises a case 1;
the top buckle of machine case 1 is connected with U type heat dissipation case 20, and U type heat dissipation case 20 internally mounted has radiator fan 21, and machine case 1 outer wall sets up the fresh air inlet 22 with U type heat dissipation case 20 looks adaptation, and machine case 1 outer wall buckle is connected with two sets of mounting panels 24, fixedly connected with filter screen 25 between two sets of mounting panels 24, and machine case 1 outer wall sets up the louvre 23 with filter screen 25 looks adaptation.
As shown in fig. 1, a first supporting plate 9 is fixedly connected inside a case 1, a first bidirectional threaded rod 2 is rotatably connected above the first supporting plate 9, a set of first moving blocks 6 are sequentially and threadedly connected to the outer wall of the first bidirectional threaded rod 2, a first L-shaped connecting rod 7 is fixedly connected to one side of each first moving block 6, a first clamping block 8 is fixedly connected to one end of each first L-shaped connecting rod 7, the first moving blocks 6 are driven by the first bidirectional threaded rod 2 to move, the first moving blocks 6 drive the first clamping blocks 8 to move through the first L-shaped connecting rods 7, and the first clamping blocks 8 move to clamp and fix one end of an aerospace control model.
As shown in fig. 1, a driving wheel 3 is fixedly connected to the outer wall of a first bidirectional threaded rod 2, a belt 4 is rotatably connected to the outer wall of the driving wheel 3, the driving wheel 3 is rotatably connected to a driven wheel 5 through the belt 4, a second bidirectional threaded rod 14 is fixedly connected to the inner wall of the driven wheel 5, a group of second moving blocks 15 are sequentially and threadedly connected to the outer wall of the second bidirectional threaded rod 14, one side of each second moving block 15 is fixedly connected to a second L-shaped connecting rod 16, one end of each second L-shaped connecting rod 16 is fixedly connected to a second clamping block 17, the tail end of each second bidirectional threaded rod 14 is rotatably connected to a second supporting plate 18, one side of each second supporting plate 18 is fixedly connected to the inner wall of a case 1, the first bidirectional threaded rod 2 drives the driving wheel 3 to rotate, the driving wheel 3 drives the driven wheel 5 to rotate through the belt 4, the driven wheel 5 drives the second bidirectional threaded rod 14 to rotate, and the second moving blocks 15 are driven by the second bidirectional threaded rod 14 to move, the second moving block 15 drives the second clamping block 17 to move through the second L-shaped connecting rod 16, and the second clamping block 17 moves to clamp and fix the other end of the space control module.
As shown in fig. 1 and 2, a sliding rod 11 is slidably connected to the inner wall of the first support plate 9, one end of the sliding rod 11 is fixedly connected with a limiting rod 12, the outer wall of the limiting rod 12 is slidably connected with the inner wall of the first support plate 9, and one end of the limiting rod 12 is connected with the outer wall of the first bidirectional threaded rod 2 in a buckling manner, so that the limiting rod 12 is conveniently clamped into the first bidirectional threaded rod 2 to limit the first bidirectional threaded rod 2;
as shown in fig. 1, a first clamping groove adapted to the U-shaped heat dissipation box 20 is formed above the chassis 1, one end of the U-shaped heat dissipation box 20 is inserted into the first clamping groove, a second clamping groove adapted to the mounting plate 24 is formed in the outer wall of the chassis 1, and the end of the mounting plate 24 is inserted into the second clamping groove, so that the U-shaped heat dissipation box 20 and the filter screen 25 can be conveniently mounted.
As shown in fig. 1, the outer wall of the first bidirectional threaded rod 2 is respectively provided with a first thread groove and a second thread groove, the first thread groove and the second thread groove are opposite threads, the outer wall of the first supporting plate 9 is provided with a first rotating groove matched with the first bidirectional threaded rod 2, and the end of the first bidirectional threaded rod 2 extends into the first rotating groove, so that the first bidirectional threaded rod 2 can rotate on the first supporting plate 9 and the first bidirectional threaded rod 2 can drive the two first moving blocks 6 to move in opposite directions.
As shown in fig. 1, the outer wall of the second bidirectional threaded rod 14 is respectively provided with a third thread groove and a fourth thread groove, the third thread groove and the fourth thread groove are opposite threads, the outer wall of the second support plate 18 is provided with a second rotating groove matched with the second bidirectional threaded rod 14, and the end of the second bidirectional threaded rod 14 extends into the second rotating groove, so that the second bidirectional threaded rod 14 can rotate on the second support plate 18 and the second bidirectional threaded rod 14 can drive the two second moving blocks 15 to move in opposite directions.
As shown in fig. 2, a sliding groove 10 adapted to the sliding rod 11 is formed in the inner wall of the first supporting plate 9, one end of the sliding rod 11 extends into the sliding groove 10, a limiting groove adapted to the limiting rod 12 is formed in the outer wall of the first bidirectional threaded rod 2, and one end of the limiting rod 12 is inserted into the limiting groove, so that the limiting rod 12 can move inside the first supporting plate 9 to fix the first bidirectional threaded rod 2.
In the embodiment, firstly, each part of the components is installed, when the component is clamped on the outer wall of the case 1 by pushing one side of the mounting plate 24, the filter screen 25 covers the heat dissipation holes 23 to filter dust in the air, so as to prevent the heat dissipation holes 23 from being blocked by dust and further reduce the heat dissipation efficiency, when the heat in the case 1 is slowly increased, the heat dissipation fan 21 can be controlled to work, the cooling fan 21 blows air into the case 1 through the air inlet hole 22, as the cooling fan 21 continuously blows out cool air to discharge the heat in the case 1 through the heat dissipation holes 23 to timely dissipate the heat in the case 1, the aerospace control modules are prevented from being damaged by high temperature, when aerospace control modules of different types are clamped and fixed, the first bidirectional threaded rod 2 is rotated to drive the first moving block 6 to move in the opposite direction, the first moving block 6 also drives the first clamping block 8 to move through the first L-shaped connecting rod 7 when moving, the first clamping block 8 moves to clamp and fix one end of the space flight control module, the first bidirectional threaded rod 2 also drives the driving wheel 3 to rotate when moving, the driving wheel 3 drives the driven wheel 5 to rotate through the belt 4, the driven wheel 5 drives the second bidirectional threaded rod 14 to rotate, the second bidirectional threaded rod 14 drives the second moving block 15 to move reversely, the second moving block 15 drives the second clamping block 17 to move through the second L-shaped connecting rod 16, the second clamping block 17 moves to clamp and fix the other end of the space flight control module, and the phenomenon that external pressure shakes the space flight control module to damage the space flight control module is avoided.
While the utility model has been described in further detail in connection with specific embodiments thereof, it will be understood that the utility model is not limited thereto, and that various other modifications and substitutions may be made by those skilled in the art without departing from the spirit of the utility model, which should be considered to be within the scope of the utility model as defined by the appended claims.
Claims (8)
1. A novel aerospace control module identification piece chassis comprises a chassis (1);
the method is characterized in that:
the top buckle of machine case (1) is connected with U type heat dissipation case (20), U type heat dissipation case (20) internally mounted has radiator fan (21), just machine case (1) outer wall set up with fresh air inlet (22) of U type heat dissipation case (20) looks adaptation, machine case (1) outer wall buckle is connected with two sets of mounting panels (24), and is two sets of fixedly connected with filter screen (25) between mounting panel (24), just machine case (1) outer wall set up with louvre (23) of filter screen (25) looks adaptation.
2. The novel aerospace control module identifier box of claim 1, wherein: the novel cabinet is characterized in that a first supporting plate (9) is fixedly connected to the inside of the cabinet (1), a first bidirectional threaded rod (2) is rotatably connected to the upper portion of the first supporting plate (9), a set of first moving blocks (6) are sequentially in threaded connection with the outer wall of the first bidirectional threaded rod (2), a first L-shaped connecting rod (7) is fixedly connected to one side of each first moving block (6), and a first clamping block (8) is fixedly connected to one end of each first L-shaped connecting rod (7).
3. The novel aerospace control module identifier box of claim 2, wherein: the outer wall of the first bidirectional threaded rod (2) is fixedly connected with a driving wheel (3), the outer wall of the driving wheel (3) is connected with a belt (4) in a rotating mode, the driving wheel (3) is connected with a driven wheel (5) in a rotating mode through the belt (4), the inner wall of the driven wheel (5) is fixedly connected with a second bidirectional threaded rod (14), the outer wall of the second bidirectional threaded rod (14) is sequentially connected with a set of second moving blocks (15) in a threaded mode, one side of each second moving block (15) is fixedly connected with a second L-shaped connecting rod (16), one end of each second L-shaped connecting rod (16) is fixedly connected with a second clamping block (17), the tail end of each second bidirectional threaded rod (14) is connected with a second supporting plate (18) in a rotating mode, and one side of each second supporting plate (18) is fixedly connected with the inner wall of the case (1).
4. The novel aerospace control module identifier box of claim 2, wherein: first backup pad (9) inner wall sliding connection has slide bar (11), slide bar (11) one end fixed connection has limiting rod (12), just limiting rod (12) outer wall with first backup pad (9) inner wall sliding connection, limiting rod (12) one end with first double-direction threaded rod (2) outer wall buckle is connected.
5. The novel aerospace control module identifier box of claim 1, wherein: a first clamping groove matched with the U-shaped heat dissipation box (20) is formed in the upper portion of the case (1), one end of the U-shaped heat dissipation box (20) is connected into the first clamping groove in an inserting mode, a second clamping groove matched with the mounting plate (24) is formed in the outer wall of the case (1), and the tail end of the mounting plate (24) is connected into the second clamping groove in an inserting mode.
6. The novel aerospace control module identifier box of claim 2, wherein: first thread groove and second thread groove have been seted up respectively to first double-direction threaded rod (2) outer wall, just first thread groove with the second thread groove is opposite screw thread, first backup pad (9) outer wall set up with the first rotatory groove of first double-direction threaded rod (2) looks adaptation, just first double-direction threaded rod (2) end extends to in the first rotatory inslot.
7. The novel aerospace control module identifier box of claim 3, wherein: the outer wall of the second bidirectional threaded rod (14) is respectively provided with a third thread groove and a fourth thread groove which are opposite threads, the outer wall of the second support plate (18) is provided with a second rotating groove matched with the second bidirectional threaded rod (14), and the tail end of the second bidirectional threaded rod (14) extends into the second rotating groove.
8. The novel aerospace control module identifier box of claim 4, wherein: the inner wall of the first supporting plate (9) is provided with a sliding groove (10) matched with the sliding rod (11), one end of the sliding rod (11) extends into the sliding groove (10), the outer wall of the first bidirectional threaded rod (2) is provided with a limiting groove matched with the limiting rod (12), and one end of the limiting rod (12) is inserted into the limiting groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122744399.2U CN216123410U (en) | 2021-11-10 | 2021-11-10 | Novel aerospace control module identification piece case |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122744399.2U CN216123410U (en) | 2021-11-10 | 2021-11-10 | Novel aerospace control module identification piece case |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216123410U true CN216123410U (en) | 2022-03-22 |
Family
ID=80715177
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122744399.2U Expired - Fee Related CN216123410U (en) | 2021-11-10 | 2021-11-10 | Novel aerospace control module identification piece case |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216123410U (en) |
-
2021
- 2021-11-10 CN CN202122744399.2U patent/CN216123410U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220322 |